Joel Susskind NASA HES Instrument Scientist NASA … · Laboratory for Atmospheres NOAA Satellite...
Transcript of Joel Susskind NASA HES Instrument Scientist NASA … · Laboratory for Atmospheres NOAA Satellite...
Results of NASA/NOAA HES Trade Studies
Joel Susskind
NASA HES Instrument Scientist
NASA GSFC
Laboratory for Atmospheres
NOAA Satellite Hyperspectral Spectrometer Workshop
March 29-31, 2011
Miami, Florida
National Aeronautics and Space Administration
www.nasa.gov
https://ntrs.nasa.gov/search.jsp?R=20110010195 2018-09-24T10:52:31+00:00Z
National Aeronautics and Space Administration Joel Susskind 2
Hyperspectral Environmental Suite (HES)
HES requirements originally called for two distinct sets of capabilities
1) IR hyperspectral sounder designed for flight on GEOS-R with comparable spectral and
radiometric performance to AIRS/CrIS
Provides information about surface and atmospheric temperature, water vapor, and
clouds
2) Inclusion of visible channels to measure ocean color
Requirement 2) was eliminated as part of trade studies designed to minimize HES cost
and risks
Three vendors BAE, BALL, and ITT were selected to conduct the HES Trade Studies
All vendors were required to evaluate both Dispersive (AIRS-like) and Interferometric (CrIS-
like) approaches for the HES IR Sounder
All vendors were also required to perform risk reduction studies
Fabricate detector arrays and laboratory spectrometers which meet HES spectral,
radiometric, operability, distortion, and crosstalk requirements
National Aeronautics and Space Administration Joel Susskind 3
Trade Studies
The vendors were required to conduct 11 Trade Studies
The goal of the trade studies was to minimize instrument cost and risk while producing
scientifically useful products
Trade Study requirements were based on a dialogue between vendors and Government
Scientists
Requirements had to be achievable from the vendor perspective
Requirements had to be compatible with at least minimal scientific needs
Trade Study 1 involved a wish list of things scientists would like from GEO orbit
All vendors showed that these would result in a very high cost/high risk instrument
Trade Study 11 was for a Reduced Accommodation Sounder (RAS)
RAS Accommodation constraints
Mass, power, volume, and data rate for RAS were compatible with flight on GEOS-R
RAS Technical constraints
RAS Spectral and radiometric requirements, as well as spatial and temporal coverage,
would result in useful scientific products
All vendors had low technical risk instrumental designs compatible with RAS constraints
National Aeronautics and Space Administration Joel Susskind 4
Accommodation Constraints for RAS for Flight on GEOS-R
Spacecraft
RAS ORIGINAL
Mass 210 kg 315 kg
Power 285 W 550 W
Volume 150 cm x 100 cm x 150 cm 170 cm x 170 cm x 150 cm
Data Rate 6.6 MBPS 66.6 MBPS
RAS instrument is smaller than originally planned
A smaller aperature results in higher noise, everything else remaining constant
HES Spectral coverage, spectral resolution, radiometric accuracy requirements were not
relaxed for RAS
Spatial coverage and revisit time requirements were all relaxed for RAS to maintain HES
radiometric accuracy
Minimal RAS requirement 3000 km x 3000 km, 10 km spatial resolution, 70 minute
revisit time – maintains current GOES Sounder coverage
National Aeronautics and Space Administration Joel Susskind 5
HES AIRS/CrIS Like Spectral Requirements
AIRS covers the spectral ranges 650 cm-1 – 1600 cm-1 and 2180 cm-1 – 2667 cm-1
AIRS resolving power /Δ ≈ 1200
AIRS Spectral resolution ranges from 0.5 cm-1 at 650 cm-1 to 2.2 cm-1 at 2667 cm-1
CrIS spectral coverage and spectral resolution are similar to AIRS
HES spectral requirement trade studies
• 650 cm-1 – 680 cm-1 Measures mid-upper stratospheric temperature
Detector performance is high risk for all designs
Spectral coverage in this region was dropped as a HES
requirement in early trade studies
• 680 cm-1 – 882 cm-1 Measures tropospheric temperature and longwave window
Required for HES
• 882 cm-1 – 1040 cm-1 Measures ozone and longwave window
Desirable but dropped as a requirement for HES
• a) 1210 cm-1 – 1645 cm-1 Measures water vapor OR
• b) 1689 cm-1 – 2150 cm-1 Measures water vapor (not on AIRS/CrIS)
a) or b) required on HES
• 2150 cm-1 – 2400 cm-1 Measures temperature profile
Technologically more challenging for interfermeter
Very desirable but not required for HES
• 2400 cm-1 – 2660 cm-1 Shortwave window
Desirable but not required for HES
National Aeronautics and Space Administration
Required for RAS Very Desirable for RAS Desirable for RAS
Tropospheric Temperature
LW Window Ozone
Water Vapor
Temperature Profile SW Window
LW Window
Joel Susskind 6
National Aeronautics and Space Administration Joel Susskind 7
Brief Overview of Vendors Trade Study 11 Designs
BAE
Dispersive Design
Covers 680 cm-1 – 1040 cm-1, 1689 cm-1 – 2410 cm-1
BALL
Dispersive Design
Covers 680 cm-1 – 893 cm-1, 1689 cm-1 – 2439 cm-1
ITT
Interferometer
Covers 680 cm-1 – 1040 cm-1, 1210 cm-1 – 1645 cm-1
All designs meet or exceed accommodation and technical requirements for RAS
Should provide AIRS quality soundings with at least 10 km resolution
The following material was made available by each vendor for this presentation
Page 8 Use or disclosure of this information is subject to the restrictions on the Title Page of this document.
Two ITT HES Design Concepts Examined in Detail
• “Reduced Accommodations” HES Sounder
– Small, reduced-aperture system (8 cm)
– ABB cornercube interferometer system (similar to GFI)
– Two infrared bands with 48x37 FPAs (DRS)
– Active cooling of FPAs
– Significant reuse of ABI components and design approaches
– Interferometer and FPAs demonstrated as part of the Hyperspectral
Imaging Test Bed (HITB) risk reduction program
• “Maximum ABI Reuse” HES Sounder (a.k.a. “ABX”)
– Essentially an ABI instrument with aft optics module removed and
replaced with an interferometer and new FPAs
– Larger volume and mass (27 cm aperture)
– Despite larger size, instrument cost and risk are actually lower than the
“Reduced Accommodation” design, due to drastic reduction in non-
recurring engineering
Page 9 Use or disclosure of this information is subject to the restrictions on the Title Page of this document.
Reduced Accommodations HES Design
Supermodule
Radiator
System
Radiator
Optical Port
Sunshield
Sensor
Electronics
IR Calibration
Telescope
SupermoduleE-W Scanner
N-S
Scanner
Optical Bench
8 cm Aperture;
ABB Interferometer
+ Y+ X
+ Z
Visible
Module
Active Cooler
Assembly
Two Infrared 48x37
FPAs (6.1-8.3um; 9.6-
14.7um)
Page 10 Use or disclosure of this information is subject to the restrictions on the Title Page of this document.
Reduced Accommodation Design is Compliant
With All Requirements
Requirement UnitsRequired
ValueTS11
Data Rate (w/ uncertainty) Mbps ≤6.6 6.2
Power, Average Operational watts ≤285 263
Mass kg ≤210 191
Width (E-W, X) cm ≤150 130
Height (N-S, Y) cm ≤100 90
Depth (Nadir-Zenith, Z) cm ≤150 95
ZRDQ Operational Zone Inner Boundary: IR-pixels degrees ≤10 9.5
ZRDQ Operational Zone Inner Boundary: Vis-pixels degrees ≤10 9.5
ZRDQ Restricted Zone Inner Boundary: IR-pixels degrees ≤3 2.9
Coverage Time: CONUS Region minutes ≤70 34.9
Long Wavelength Resolution cm-1 0.875 0.875
Mid Wavelength Resolution cm-1 1.75 1.75
Maximum GSA at SSP for DS-IR Bands rad ≤280280.0 N/S x
272.6 E/W
Maximum GSA at SSP for DS-VIS Band rad ≤35 33.2
DOEE: DS-IR - Weighted Minimum Band % ≥70 71
LW Band NEdN - Minimum Margin % ≥30 31
MW Band NEdN - Minimum Margin % ≥30 35
Adjacent Pixels Simultaneity, CONUS minutes ≤10 4.1
Absolute Radiometric Accuracy (Max of LW or MW) K
≤1 or
Derived
NEdT
0.86
Sounder Spectral Stability over any 24 hr period -
Maximum
% channel
width<2 0.29
Sounder Spectral Bands Simultaneity (Vis to IR) seconds ≤10 3.81
HES Design
Page 11 Use or disclosure of this information is subject to the restrictions on the Title Page of this document.
“Maximum ABI Reuse” HES Design
Performance is
Superior to Reduced
Accommodation
Design
New Hyperspectral Aft Optics
(HAO) Module
ABI Aft Optics
Module is
Replaced by a
Hyperspectral
Module
(Interferometer
or Dispersive
Technologies
Are Both
Compatible)
Virtually No Other
Changes to ABI
Design or Hardware
27 cm Aperture,
Two Infrared
96x96 FPAs
Page 12 Use or disclosure of this information is subject to the restrictions on the Title Page of this document.
Risk Reductions Eliminated Key Risks for Both Designs
HITB Demonstrated 96x96 FPAs,
Cooled Cornercube Interferometer,
New Aft Optics, and New Signal
Processing Electronics Design
ABI PTM Has Demonstrated
Active Coolers, Scanner,
Fore-Optics, Structure, Control
Electronics, and GEO Thermal
Control
Ball Aerospace Baseline Design -
Spacecraft Resources
Spacecraft
Resource
Simplified
Sounder
Allocation
Compliant
With Margin
Mass (Mature) <210 kg Y
Power (Mature) <285 W Y
Data Rate (No
compression)<6.6 Mbps Y
Sensor Unit
Envelope<1.1 x 1 x 1.5 m3 Y
Ball Aerospace Design Meets the Reduced
Capability Spacecraft Accommodations with Margin
Ball Aerospace Simplified Sounder Design -
Performance Against Driving Requirements
Drivers Requirement Compliant
With Margin
Coverage Time (CONUS) < 70 minutes Y
Co-Reg Channel Overlap > 90% Y
Ground Sample Distance < 10 x 10 km2 Y
Spectral Range
11.34-14.7 m AND
4.64-5.92 m OR
6.08-8.26 m
Y
NEdT (@12.5 m) < 0.18 K Y
Absolute Accuracy < 1 K Y
Spectral Resolution (@ 12.5 m) < 14.59 nm Y
DOEE > 70% Y
Ball Aerospace Design Meets all Performance Driving
Requirements with Margin
Ball Aerospace Simplified Sounder Concept
Single slit, reflective grating spectrometer
Unique folding of two spectral regions onto a single focal plane using a
spatial-split dichroic assembly
Wavelength Dimension
Sp
atia
l D
ime
nsio
n Focal Plane
Wavelength Range #1
Wavelength Range #2
Applicable Ball Aerospace Technology
Demonstrations
Spatial Split
Dichroic Assy
T-Vac
chamber
Thermal
Window
Mount
Position Mirror
Auto-collimator
Guinness spectrometer
H/W & Test
Camera Assemblies
Flight-like FPA Cables
SB235-E Cryo-Cooler
Compressor
BB H/W & Test
Focal Plane Electronics
H/W & Test
Filter Assembly Test
Scan Mech H/W & Test
Optical Component H/W & Test
Project Guinness Highlights
Guinness is a demo of critical components for a multi-
channel imaging spectrometer (9-14 m)
Project started in April 2005 – Testing completed June
2006 (15 months)
Demonstrates an IR imaging spectrometer operating at
cryogenic temperatures with critical components
Primary motivation: Burn down percieved technical risk
of co-registration between multiple spectrometer
channels
H/W designed, developed, & tested in 15 months
Test set and methodology developed concurrently for rapid & accurate
performance testing of imaging spectrometers
Spectral Pixel
Spa
tial P
ixel
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ixel
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Co-registration of 0.06 pixels between 2 spectrometer channels attained
Contains BAE SYSTEMS Proprietary Information-Approved for ReleaseFuture Sounding and GHG Sensor Workshop
Date: March,2011
HES 169.5 cm
(Req.=170 cm)
140.6 cm
(Req.=170 cm)
149.0 cm
(Req.= 150 cm)
X
ZY
GOES RA
Sounder
150.0
cm
92.5
cm
140.0 cm X
ZY
Reduced-Accommodations IR Sounder and HES Comparison
Shared Characteristics• Spectral Coverage:
– 4.165-5.92 m (1689-2400 cm-1)
– 9.65-14.7 m (680-1036 cm-1)
• Spectral Resolution: / >1000
• NE T: 0.2K
• Spectral Stability: <0.01
HES Characteristics• Mass: 214 kg
• Power: 326 W
• Data Rate: 7.3 Mbps
• SW/M Coverage Rate: – CONUS/hr @ 5 km GSD
• Disk Sounding Coverage Rate: – 62 Deg. Disk/hr @ 10 km GSD
GOES-R Sounder Characteristics• Mass: 169 kg
• Power: 223 W
• Data Rate: 1.8 Mbps
• CONUS Sounding Coverage Rate: – CONUS/hr @ 10 km GSD
(Can Provide 2x CONUS/Hr also)
• Disk Sounding Coverage Rate: – 62 Deg. Disk/hr @ 20 km GSD
• Meso-scale Demonstration @ 5 km
Contains BAE SYSTEMS Proprietary Information-Approved for ReleaseFuture Sounding and GHG Sensor Workshop
Date: March,2011
Key TRL Assessment Summary @ HES FPCCR
-All Technologies at Level Needed For Low-Risk HES Development
Technology
Area
Technology Maturation Plan
Special
Grating
End-to-end cryo-testing in Sounder
Spectrometer
Special FPA Optical Filter
Build and test HES Prototype (“smile”,
off-axis rejection, radiation etc.)
PMA Encoder Test in Pointing Stability test bed to
validate performance at low angular
rates
0
1
2
3
4
5
6
7
8
9
Cryo StructurePassive
Rad.
IRFPA Dewar Optics
Cov.
Act.
A/D Conv.Spect.
Pre-
Filter
PMA
Afocal
Focus
Adjust
Mech.
PMA
Motors /
Bearings
Spec.
Mirror
Front
Telescope
Grating Linear
Variable
Filter
Encoder
TR
L
Fully-Compliant Flight-Like VLWIR FPA
Demonstration Has Retired the
Technology Risk for the HES Flight FPA
National Aeronautics and Space Administration Joel Susskind 20
Summary
• NASA/NOAA HES Trade studies were completed in 2007
Three vendors each had low technical risk, affordable cost designs for a
Reduced Accommodation Sounder (RAS) compatible with flight on GOES R-U
RAS would deliver AIRS quality soundings with spatial and temporal coverage at least as
good as now achieved with the current IR Geo Sounder
• NASA was prepared to down select to a single vendor to proceed to CDR
• NOAA terminated the study because of instrument cost and risk concerns
NOAA also considered the ground system very high risk for HES
RAS data rate requirement is now 6.6 MBPS compared to 66.6 MBPS as originally
specified
This data rate is only slightly larger than AIRS data rate
Ground system should not be a concern
The three vendors are all enthusiastic about continuing work to design and build HES